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Full text of "XB-52 Stratofortress 2nd Article Characteristics Summary 23 December 1949"

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EXPERIMENTAL 



BOMBER - 



- XB-52 






n 






B 




ooo 






BOEING 



Wing area " 4000 sq ft 

Span 185.0 ft 



Length 143.1 ft 

Height 46.2 ft 



AVAILABILITY 


PROCUREMENT 


Number available 


Number to be delivered in fiscal years 


ACTIVE 


RESERVE 


TOTAL 

























STATUS 



PRE LIMINARY 



1. Design initiated: 27 October 1948 

2. Mock-up inspection: 26 April 1949 

3. Engineering acceptance inspection: April 1951 (estimated) 

4. First flight: 1st article (with J40 engines), June 1951 (estimated); 2 nd article, December 
1951 (estimated) 

5. Construction has been initiated. 

6. First article (stripped) will utilize J40-WE-6 for preliminary flight tests. YJ57-P-3 will 
be installed in second article. However, tentative plans call for reworking this engine into 

a future model of higher rating as shown below. 



POWER PLANT 



(8)XJ57-P-( ) 
Pratt-Whitney 
ENGINE RATINGS 
S.L. Static LB - RPM 

Max: 9250 - 

Mil: 9250 - 

Nor: 8600 - 



Note: All performance based 
on above ratings 



FEATURES 



Crew: 5 
Cabin Pressurization 
Bombing -Navig. Radar 
Gun-Laying Radar 
K-l Bombing System 
Quadricycle Landing Gear 
Vertical Camera Station 
Braking Parachute 
ATO: 4x4 to 5000 lb (60 

seconds) 
Max Fuel Capacity: 

28,670 gal 



ARMAMENT 



Turrets: 1 

Guns: (2) .50 cal 

Ammunition (tot): 1200 rds 

Max Bomb Load: 25,000 lb 

Max Bomb Size: 25,000 lb 



23 DEC. 1949 



SECRET (SECOND ARTICLE)XB" 52 



EXPERIMENTAL 



S m\SU>i<* 



XB-52 



58,000 FT 

! — — ~j _ 

/ 

A/41,400 FT" 



49,700 FT 



COMBAT RADIUS= 2 66 Nautical Mile; 



PERFORMANCE 


i— -aw. w m& BB eat mmm gn> w ok, mm mra> 

COMBAT RADIUS 


COMBAT RANGE 


COMBAT SPEED 


2 O 6 naut. mi 
with 10,000 lb pay load 
at 453 knots avg. 
in 11.9 hours. 


L I \y naut. mi 

with 10,000 lb payload 
at 456 knots avg. 
in 11.7 hours. 


knots at 

35,000 ft alt, max power 


MAXIMUM SPEED 


5 »3 ^3 knots at 
20,000 ft alt, max power 


CLIMB 


CEILING 


TAKE-OFF 


3000 <p» 

sea level, take-off weight 
normal power 


43,500 . 

100 fpm, take-off weight 
normal power 


groun 

5 3 ft 

no assist 


d run 

assisted 


5300 

sea level, combat weight 
maximum power 


49,400 „ 

500 fpm, combat weight 
maximum power 


over 50 f 

5 6 3 ft 

no assist 


t height 

assisted 


LOAD 


WEIGHTS 


STALLING SPEED 


Bombs: 10,000 lb 
Ammunition: 

1200 rds/.50 cal 

Fuel: 27,417 gal 
protected 73 % 
droppable % 
external % 


Empty 152,300 lb 
Combat... 228,900 lb 
Take - off 330,000 lb 
limited by strength 


1 1 7 

1 1 1 knots 
flaps down, take-off weight 


TIME TO CLIMB 





NOTES 



1. PERFORMANCE BASIS: 

(a) Estimated data 

(b) Fuel density: 6.0 lb/gal 

(c) In computing Radius and Range, specific fuel consumptions have been increased 5% to al- 
low for variations of fuel flow in service aircraft. 

(d) Variable exit tail pipe version of Pratt-Whitney XJ57-P-1 engine specification No. A- 
1620, dated 26 May 1949 

2. REVISION BASIS: To reflect change in max fuel capacity, length of fuselage and clarifi- 
cation of development status. 



WF-O-28 JUNE 49 500 



XB- 52(SEC0ND ARTICLE) 



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Ohio 45433 r °rce Base